That is not an extraordinary challenge especially considering it has been accomplished already, despite your denials of ignorance and incredulity.
No, the Challenge has not been accomplished by anyone. Why do you lie about it?
Noone is able to describe the fuel used for a manned space trip to Mars and how to get it off the ground, etc. Noone has not even described the spacecraft to be used and its mass. Shall it be a tinpot with no facilities or something more comofortable. What is its mass without fuel? And how to get it off the ground?
That's the Challenge.
Stupid peopel think that as I can launch a 300 kg satellite into orbit, they can launch a 100 000 kg manned spacecraft to Mars. But it is not the same thing. And they cannot even calculate the fuel for it.
NASA has announced they do not have the hardware for it. Their rockets are too weak. But the rockets will become strong 2037! LOL. NASA does not even have the software to calculate the fuel!! NASA is really a joke.
Still just going to ignore this:
Saturn V
Individual stage Total vessel
STAGE Total mass Dry mass Total mass Dry mass Isp Delta-v
1 LOX/RP-1 2,300,000 131,000 2,900,000 731,000 263s 3554.2 m/s
2 LOX/LH 480,000 36,000 600,000 156,000 421s 5561.5 m/s
3 LOX/LH 120,800 10,000 120,800 10,000 421s 8796.2 m/s
--------------
17911.9 m/s
Masses are in kg
Does not include delta-v calculations for the lunar lander but assumes the gross weight of the Saturn V.
The above is using information found here:
https://en.wikipedia.org/wiki/Saturn_V and on your site.
Making a round trip from the Earth to a lunar orbit takes about 17,500 m/s. It can be done with a little less.




Explanation of methodology used:
http://www.braeunig.us/space/index.htmSince you could not do the calculation your self:
kg of propellant used per second= Thrust in Newtons/ISP in meters per second
Stage 1:
34,020,000/2580= 13,186 kg per second
164 second burn time.
TWR of the Saturn V on the pad:
5 F-1 engines with 6.672.000 N thrust each=33,360,000 N
2 896 895 kg gross rocket mass
(6,672,000N*5)/(2,896,895*9. 8 )=1.17 TWR
Means the rocket can lift off the pad.
Can you show me where the above is wrong? Can you show the the proper way to do the calculations? How about just show me the proper way to calculate TWR?
How about answering my questions about you challenge? Surely that is on topic. Did you miss my post with the questions?
Here you can get what you claim NASA does not have access to:
http://opensource.gsfc.nasa.gov/projects/emtg/index.phpIt is open source, but you do need 3rd party software to run it that cost $350.